EP2618052A1 - Buse de combustible - Google Patents

Buse de combustible Download PDF

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Publication number
EP2618052A1
EP2618052A1 EP20130152025 EP13152025A EP2618052A1 EP 2618052 A1 EP2618052 A1 EP 2618052A1 EP 20130152025 EP20130152025 EP 20130152025 EP 13152025 A EP13152025 A EP 13152025A EP 2618052 A1 EP2618052 A1 EP 2618052A1
Authority
EP
European Patent Office
Prior art keywords
fuel
flow
air
nozzle
fuel nozzle
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP20130152025
Other languages
German (de)
English (en)
Inventor
Arvind Venugopal Menon
llya Aleksandrovich SLOBODYANSKIY
Abinash Baruah
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2618052A1 publication Critical patent/EP2618052A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/383—Nozzles; Cleaning devices therefor with swirl means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • F23D11/386—Nozzle cleaning
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply

Definitions

  • a gas turbine engine may employ one or more fuel nozzles to facilitate fuel-air mixing in a combustor.
  • Each fuel nozzle may direct a flow of fuel, a flow of air, and optional flows of other fluids into the combustor for combustion therein.
  • a combustion flame may flash back and/or hold to a surface of the fuel nozzle. Flame holding may cause significant damage to the fuel nozzles and/or reduce the performance of the fuel nozzles and the overall gas turbine engine.
  • flame holding may occur if a flammable fuel-air mixture resides in a low velocity region in close proximity to a combustion source.
  • low velocity regions generally may be found near the interior walls of the fuel nozzles due to the aerodynamics therein.
  • Such a flammable mixture potentially may result in flame holding inside the fuel nozzles. Flame holding inside fuel nozzles may result in the fuel nozzles burning out, i.e ., experiencing flame damage therein.
  • the present invention provides an example of a fuel nozzle for mixing a flow of fuel and a flow of air.
  • the fuel nozzle may include a downstream face, a number of fuel passages positioned about the downstream face for the flow of fuel, and a nozzle collar position about the downstream face.
  • the nozzle collar may include a number of air vanes for the flow of air and one or more purge holes therethrough.
  • the present invention further provides an example of a combustor for use with a gas turbine engine.
  • the combustor may include a combustion chamber and a number of fuel nozzles positioned about the combustion chamber.
  • Each of the fuel nozzles may include a nozzle collar thereon.
  • the nozzle collar may include one or more air vanes with one or more purge holes for a flow of purge air therethrough.
  • Fig. 1 shows a schematic view of gas turbine engine 10 as may be used herein.
  • the gas turbine engine 10 may include a compressor 15.
  • the compressor 15 compresses an incoming flow of air 20.
  • the compressor 15 delivers the compressed flow of air 20 to a combustor 25.
  • the combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35.
  • the gas turbine engine 10 may include any number of combustors 25.
  • the flow of combustion gases 35 is in turn delivered to a turbine 40.
  • the flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.
  • Other configurations and other components may be used herein.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • Other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • Fig. 2 shows an example of the combustor 25 that may be used with the gas turbine engine 10 and the like.
  • the combustor 25 may include a number of fuel nozzles 55 therein. As described above, each of the fuel nozzles 55 may direct a flow of air 20, a flow of fuel 30, and optional flows of other fluids into the combustor 25 for combustion therein. Any number of the fuel nozzles 55 may be used in any configuration.
  • the fuel nozzles 55 may be attached to an end cover 60 near a head end 65 of the combustor 25. The flows of air 20 and fuel 30 may be directed through the end cover 60 and the head end 65 to each of the fuel nozzles 55 so as to distribute a fuel-air mixture therein.
  • the combustor 25 also may include a combustion chamber 70 therein.
  • the combustion chamber 70 may be defined by a combustion casing 75, a combustion liner 80, a flow sleeve 85, and the like.
  • the liner 80 and the flow sleeve 85 may be coaxially positioned with respect to one another so as to define an air pathway 90 for the flow of air 20 therethrough.
  • the combustion chamber 70 may lead to a downstream transition piece 95.
  • the flows of air 20 and fuel 30 may mix downstream of the fuel nozzles 55 for combustion within the combustion chamber 70.
  • the flow of combustion gases 35 then may be directed via the transition piece 95 towards the turbine 40 so as to produce useful work therein.
  • Other components and other configuration also may be used herein.
  • the fuel nozzle 100 may include an outer tube 110.
  • the outer tube 110 may lead to a downstream face 120 with a fuel nozzle tip 130.
  • the outer tube 110 may include a number of fuel and air passages therein. Specifically, a number of fuel passages 140 may extend therethrough and may be axially positioned about the downstream face 120.
  • the fuel passages 140 may be in communication with the flow of fuel 30.
  • a number of tip outlets 150 also may extend therethrough and may be positioned about the fuel nozzle tip 130.
  • the tip outlets 150 may be in communication with the flow of fuel 30, the flow of air 20, or other types of flows.
  • the flows of fuel 30 extending through the fuel passages 140 and through the tip outlets 150 may be the same and/or different types of fuel flows depending upon the nature of the combustion and other types of parameters. Other components and other configurations also may be used herein.
  • a number of recirculation zones 190 may be formed as a result of the interaction between the flows of air 20 and fuel 30. These recirculation zones 190 may lead to flame holding about the fuel nozzle 100 via a region of low velocity.
  • a number of purge holes 200 may be positioned through the air vanes 170.
  • the purge holes 200 may have any size, shape, or configuration. Any number of the purge hole 200 may be used herein.
  • the purge holes 200 may be angled and/or multiple angles may be used herein. Additional purge holes 200 also may extend through the downstream ring 180 and/or elsewhere. Other components and other configurations may be used herein.
  • the purge holes 200 thus provide for a flow of purge air 210 therethrough as part of the overall flow of air 20.
  • the flow of purge air 210 through the purge holes 200 may disrupt the recirculation zones 190 downstream of the fuel nozzles 100 caused by the regions of low velocity or otherwise.
  • the purge holes 200 may be angled such that the purge air 210 disrupts the creation of the recirculation zones 190 in a substantially circumferential direction. Elimination or reduction of these recirculation zones 190 along the circumferential direction should reduce flame holding thereon. As such, the reduction in flame holding should provide the fuel nozzle 100 with improved durability and lifetime.
  • the overall gas turbine engine 100 may have improved emissions and overall improved performance.
  • the use of the purge holes 200 with the flow of purge air 210 therethrough may be original equipment or added as part of a retrofit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
EP20130152025 2012-01-23 2013-01-21 Buse de combustible Withdrawn EP2618052A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/355,580 US20130189632A1 (en) 2012-01-23 2012-01-23 Fuel nozzel

Publications (1)

Publication Number Publication Date
EP2618052A1 true EP2618052A1 (fr) 2013-07-24

Family

ID=47563290

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20130152025 Withdrawn EP2618052A1 (fr) 2012-01-23 2013-01-21 Buse de combustible

Country Status (5)

Country Link
US (1) US20130189632A1 (fr)
EP (1) EP2618052A1 (fr)
JP (1) JP2013148341A (fr)
CN (1) CN103216849A (fr)
RU (1) RU2013102632A (fr)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2940389A1 (fr) * 2014-05-02 2015-11-04 Siemens Aktiengesellschaft Agencement de brûleur de combustion
US9803552B2 (en) 2015-10-30 2017-10-31 General Electric Company Turbine engine fuel injection system and methods of assembling the same
US10775048B2 (en) * 2017-03-15 2020-09-15 General Electric Company Fuel nozzle for a gas turbine engine
CN107166435A (zh) * 2017-07-07 2017-09-15 西安富兰克石油技术有限公司 一种多燃料喷嘴、燃料喷出系统及其涡轮发动机
US11680709B2 (en) * 2020-10-26 2023-06-20 Solar Turbines Incorporated Flashback resistant premixed fuel injector for a gas turbine engine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6311496B1 (en) * 1997-12-19 2001-11-06 Alstom Gas Turbines Limited Gas turbine fuel/air mixing arrangement with outer and inner radial inflow swirlers
EP1243854A1 (fr) * 2001-03-09 2002-09-25 ALSTOM (Switzerland) Ltd Injecteur de carburant
EP1867925A1 (fr) * 2006-06-12 2007-12-19 Siemens Aktiengesellschaft Brûleur
US20080000234A1 (en) * 2006-06-29 2008-01-03 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor
US20110005189A1 (en) * 2009-07-08 2011-01-13 General Electric Company Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle

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US5193346A (en) * 1986-11-25 1993-03-16 General Electric Company Premixed secondary fuel nozzle with integral swirler
US5345768A (en) * 1993-04-07 1994-09-13 General Electric Company Dual-fuel pre-mixing burner assembly
EP0935097B1 (fr) * 1998-02-09 2004-09-01 Mitsubishi Heavy Industries, Ltd. Chambre de combustion
US6082113A (en) * 1998-05-22 2000-07-04 Pratt & Whitney Canada Corp. Gas turbine fuel injector
US6547163B1 (en) * 1999-10-01 2003-04-15 Parker-Hannifin Corporation Hybrid atomizing fuel nozzle
US6655145B2 (en) * 2001-12-20 2003-12-02 Solar Turbings Inc Fuel nozzle for a gas turbine engine
US7000403B2 (en) * 2004-03-12 2006-02-21 Power Systems Mfg., Llc Primary fuel nozzle having dual fuel capability
US7251940B2 (en) * 2004-04-30 2007-08-07 United Technologies Corporation Air assist fuel injector for a combustor
JP4070758B2 (ja) * 2004-09-10 2008-04-02 三菱重工業株式会社 ガスタービン燃焼器
US7237730B2 (en) * 2005-03-17 2007-07-03 Pratt & Whitney Canada Corp. Modular fuel nozzle and method of making
EP1821035A1 (fr) * 2006-02-15 2007-08-22 Siemens Aktiengesellschaft Brûleur de turbine à gaz et procédé pour mélanger le carburant et l'air dans une zone de tourbillonage d'un brûleur de turbine à gaz
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US8186165B2 (en) * 2009-03-16 2012-05-29 General Electric Company Turbine fuel nozzle having heat control
US8256226B2 (en) * 2009-04-23 2012-09-04 General Electric Company Radial lean direct injection burner
US20100281869A1 (en) * 2009-05-06 2010-11-11 Mark Allan Hadley Airblown Syngas Fuel Nozzle With Diluent Openings
US8607570B2 (en) * 2009-05-06 2013-12-17 General Electric Company Airblown syngas fuel nozzle with diluent openings
US8359870B2 (en) * 2009-05-12 2013-01-29 General Electric Company Automatic fuel nozzle flame-holding quench
US20110107769A1 (en) * 2009-11-09 2011-05-12 General Electric Company Impingement insert for a turbomachine injector
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US20120208136A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US20120208135A1 (en) * 2011-02-11 2012-08-16 General Electric Company System and method for operating a combustor
US9371989B2 (en) * 2011-05-18 2016-06-21 General Electric Company Combustor nozzle and method for supplying fuel to a combustor
US8978384B2 (en) * 2011-11-23 2015-03-17 General Electric Company Swirler assembly with compressor discharge injection to vane surface

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6311496B1 (en) * 1997-12-19 2001-11-06 Alstom Gas Turbines Limited Gas turbine fuel/air mixing arrangement with outer and inner radial inflow swirlers
EP1243854A1 (fr) * 2001-03-09 2002-09-25 ALSTOM (Switzerland) Ltd Injecteur de carburant
EP1867925A1 (fr) * 2006-06-12 2007-12-19 Siemens Aktiengesellschaft Brûleur
US20080000234A1 (en) * 2006-06-29 2008-01-03 Snecma Device for injecting a mixture of air and fuel, and combustion chamber and turbomachine provided with such a device
US20090111063A1 (en) * 2007-10-29 2009-04-30 General Electric Company Lean premixed, radial inflow, multi-annular staged nozzle, can-annular, dual-fuel combustor
US20110005189A1 (en) * 2009-07-08 2011-01-13 General Electric Company Active Control of Flame Holding and Flashback in Turbine Combustor Fuel Nozzle

Also Published As

Publication number Publication date
RU2013102632A (ru) 2014-07-27
JP2013148341A (ja) 2013-08-01
CN103216849A (zh) 2013-07-24
US20130189632A1 (en) 2013-07-25

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